Base Stations Including Integrated Systems For Servicing UAVs

ABSTRACT

A base station is disclosed for use with an unmanned aerial vehicle (UAV). The base station includes: an enclosure; a cradle that is configured to charge a power source of the UAV during docking with the base station; and a temperature control system that is connected to the cradle and which is configured to vary temperature of the power source of the UAV. The temperature control system includes: a thermoelectric conditioner (TEC); a first air circuit that is thermally connected to the TEC and which is configured to regulate temperature of the TEC; and a second air circuit that is thermally connected to the TEC such that the TEC is located between the first air circuit and the second air circuit. The second air circuit is configured to direct air across the cradle to thereby heat or cool the power source of the UAV when docked with the base station.

CROSS-REFERENCE TO RELATED APPLICATION(S)

This application claims the benefit of and priority to U.S. ProvisionalApplication No. 63/294,148, filed Dec. 28, 2021, U.S. ProvisionalApplication No. 63/255,566, filed Oct. 14, 2021, and U.S. ProvisionalApplication No. 63/222,768, filed Jul. 16, 2021, the disclosures ofwhich are hereby incorporated by reference in their entirety.

TECHNICAL FIELD

The present disclosure relates to a base station (dock) for an unmannedaerial vehicle (UAV) (e.g., a drone). More specifically, the presentdisclosure relates to a base station that includes a series ofintegrated systems, which allow for automated servicing (e.g., docking,storage, charging, operation, etc.) and accommodation of a UAV.

BACKGROUND

In an attempt to manage various environmental settings and/or scenarios(e.g., temperature, precipitation, humidity, etc.), known base stationstypically include a series of conditioning systems, which mandates theuse of an enclosure that often drastically exceeds the size of theUAV(s) being serviced and/or accommodated. Additionally, conventionaldocking procedures often require the connection of a UAV to an externalpower supply during recharging or exchange of the UAV's power sourceitself. As a result, known base stations are often large, mechanicallycomplex, and expensive.

The present disclosure addresses these deficiencies, among others, andprovides a base station that offers improved servicing of UAVs andsignificant size reductions that allow for more efficient operation andsubstantial cost savings.

SUMMARY

In one aspect of the present disclosure, a base station is disclosedthat is configured for use with an unmanned aerial vehicle (UAV). Thebase station includes: an enclosure; a cradle that is configured forelectrical connection to a power source of the UAV during docking tofacilitate charging of the power source; and a temperature controlsystem that is connected to the cradle and which is configured to varytemperature of the power source of the UAV. The cradle is movablebetween a retracted position, in which the cradle is positioned withinthe enclosure, and an extended position, in which the cradle ispositioned externally of the enclosure to facilitate docking with theUAV. The temperature control system includes: a thermoelectricconditioner (TEC) having a first end and a second end; a first aircircuit that is thermally connected to the TEC and which is configuredto regulate temperature of the TEC; and a second air circuit that isthermally connected to the TEC such that the TEC is located between thefirst air circuit and the second air circuit. The second air circuit isconfigured to direct air across the cradle to thereby heat or cool thepower source of the UAV when docked with the base station.

In various embodiments, the temperature control system may be configuredto cool the power source of the UAV (e.g., when the base station and theUAV are used in warmer environments) or to heat the power source of theUAV (e.g., when the base station and the UAV are used in coolerenvironments).

In certain embodiments, the first air circuit may be configured as anopen system and the second air circuit may be configured as a closedsystem.

In certain embodiments, the TEC may be configured as a Peltier system.

In certain embodiments, the first air circuit may include: a firstplenum; a first heat sink that is connected to the first plenum and thefirst end of the TEC; and a first air circulator that is configured todirect air through the first plenum and across the first heat sink tovary air temperature within the first air circuit and thereby regulatethe temperature of the TEC.

In certain embodiments, the second air circuit may include: a secondplenum; a second heat sink that is connected to the second plenum andthe second end of the TEC; and a second air circulator that isconfigured to direct air through the second plenum and across the secondheat sink to vary air temperature within the second air circuit andthereby heat or cool the power source of the UAV when docked with thebase station.

In certain embodiments, the temperature control system may be configuredto cool the power source of the UAV when docked with the base station.

In certain embodiments, the second plenum may define an air inlet and anair outlet.

In certain embodiments, the air inlet may be configured to direct airinto the cradle and across the power source of the UAV and the airoutlet may be configured to receive the air directed across the powersource of the UAV and redirect the air across the second heat sink.

In certain embodiments, the second plenum may include a first sectionand a second section that is movable in relation to the first section.

In certain embodiments, the first section may be connected to the TECand the second section may be connected to the cradle.

In certain embodiments, the first section and the second section may beconfigured for mating engagement upon movement of the cradle into theretracted position.

In another aspect of the present disclosure, a base station is disclosedthat is configured for use with a UAV. The base station includes atemperature control system that is configured to vary temperature of theUAV. The temperature control system includes: a thermoelectricconditioner (TEC); an open air circuit that is thermally connected tothe TEC and which is configured to regulate temperature of the TEC; anda closed air circuit that is thermally connected to the TEC such thatthe TEC is located between the open air circuit and the closed aircircuit. The closed air circuit is configured to direct air across theUAV when docked with the base station.

In certain embodiments, the temperature control system may be configuredto heat or cool the UAV subject to environmental conditions.

In certain embodiments, the closed air circuit may include a firstsection and a second section that is movable in relation to the firstsection.

In certain embodiments, the base station may further include a cradlethat is configured for electrical connection to the UAV during dockingto facilitate charging of the UAV.

In certain embodiments, the cradle may be extendable from andretractable into the base station.

In certain embodiments, the first section of the closed air circuit maybe connected to the TEC and the second section of the closed air circuitmay be connected to the cradle.

In certain embodiments, the first section and the second section may beconfigured for mating engagement upon retraction of the cradle into thebase station.

In another aspect of the present disclosure, a method is disclosed forregulating the temperature of a power source in a UAV. The methodincludes: docking the UAV within a cradle of a base station; retractingthe cradle into the base station; and directing thermally conditionedair across the power source of the UAV via an air circuit that isconnected to the cradle.

In certain embodiments, the method may further include directing airacross a heat sink that is thermally connected to a thermoelectricconditioner (TEC) to treat the air prior to direction across the powersource of the UAV.

In certain embodiments, directing air across the heat sink may includecirculating the air through a plenum that is connected to the heat sink.

In certain embodiments, retracting the cradle into the base station mayinclude closing the air circuit.

In certain embodiments, closing the air circuit may include mating afirst section of the plenum with a second section of the plenum.

In certain embodiments, the first section of the plenum may be connectedto the TEC and the second section of the plenum may be connected to thecradle.

In another aspect of the present disclosure, a base station is disclosedthat is configured for use with a UAV. The base station includes: anouter housing that defines a roof section; an inner housing that isconnected to the outer housing; one or more heating elements that aresupported by the enclosure and which are configured to heat the roofsection; at least one fiducial that is supported by the enclosure; anillumination system that is supported by the enclosure and which isconfigured to illuminate the at least one fiducial; and a visualizationthat is supported by the enclosure.

In certain embodiments, the enclosure (e.g., the outer housing) maydefine at least one channel that is configured to direct water in amanner that inhibits entry into the base station.

In certain embodiments, the base station may further include one or moretemperature sensors that are in communication with the one or moreheating elements such that the one or more heating elements areactivated upon receiving a signal relayed by the one or more temperaturesensors indicating that temperature has crossed a threshold.

In certain embodiments, the at least one fiducial may include a firstfiducial and a second fiducial, each of which is supported by the roofsection.

In certain embodiments, the second fiducial may be removably connectedto the roof section.

In certain embodiments, the first fiducial may define a first surfacearea, and the second fiducial may define a second surface area that isless than the first surface area.

In certain embodiments, the first surface area may lie substantiallywithin the range of (approximately) 40 percent to (approximately) 80percent of a surface area defined by the roof section.

In certain embodiments, the second surface area may lie substantiallywithin the range of (approximately) 10 percent to (approximately) 50percent of the first surface area.

In certain embodiments, the illumination system may include one or morelight sources that are secured to the roof section and which areconfigured to light the first fiducial and the second fiducial.

In certain embodiments, the illumination system may be configured tostrobe the one or more light sources according to a pattern that isrecognizable by the UAV during approach to thereby identify the basestation.

In certain embodiments, the visualization system may include a digitalimage capturing device that is configured to identify precipitation andactuate the one or more heating elements.

In certain embodiments, the base station may further include at leastone status indicator that is supported by the enclosure (e.g., the outerhousing).

In certain embodiments, the base station may further include at leastone internal fan to regulate temperature and/or humidity within the basestation.

In certain embodiments, the at least one internal fan may be supportedby at least one of the outer housing and the inner housing.

In another aspect of the present disclosure, a base station is disclosedthat is configured for use with a UAV. The base station includes: anenclosure; a door that is movably connected to the enclosure such thatthe door is repositionable between a closed position and an openposition; and one or more actuators that extend between the door and theenclosure. The enclosure includes an outer housing and an inner housingthat is connected to the outer housing and which defines an internalcavity that is configured receive the UAV. Each actuator includes amotor assembly and a linkage assembly that extends between the motorassembly and the door. The motor assembly is secured to the innerhousing such that the motor assembly is located between the outerhousing and the inner housing, and the linkage assembly extends throughthe inner housing.

In certain embodiments, the linkage assembly may include: a drive screwthat is operatively connected to the motor assembly such that actuationof the motor assembly causes rotation of the drive screw; a carrier thatis threadably engaged to the drive screw such that rotation of the drivescrew causes axial translation of the carrier; a first arm; and a secondarm.

In certain embodiments, the first arm may have a first end that ispivotably connected to the carrier and a second end, and the second armmay have a first end that is pivotably connected to the second end ofthe first arm and a second end that is pivotably connected to the door.

In certain embodiments, the base station may further include a bracketthat is fixedly connected to the door.

In certain embodiments, the bracket may be pivotably connected to thesecond end of the second arm.

In certain embodiments, the drive screw may be configured such thatrotation of the drive screw in a first direction causes advancement ofthe carrier towards the door and rotation of the drive screw in a seconddirection causes advancement of the carrier away from the door.

In certain embodiments, the drive screw may include threading defining apitch that is configured to inhibit force transmission from the door tothe carrier to thereby maintain the door in the closed position.

In another aspect of the present disclosure, a base station is disclosedthat is configured for use with an unmanned aerial vehicle (UAV). Thebase station includes: an enclosure defining an internal cavity that isconfigured to receive the UAV; a first fiducial that is supported by aroof section of the enclosure and which defines a first surface area; asecond fiducial that is supported by the roof section of the enclosureand which defines a second surface area that is less than the firstsurface area; and an illumination system that is supported by roofsection and which is configured to illuminate the first fiducial and thesecond fiducial.

In certain embodiments, the second fiducial may be configured forremovable connection to the roof section.

In certain embodiments, the first surface area may lie substantiallywithin the range of (approximately) 40 percent to (approximately) 80percent of a surface area defined by the roof section.

In certain embodiments, the second surface area may lie substantiallywithin the range of (approximately) 10 percent to (approximately) 50percent of the first surface area.

In certain embodiments, the illumination system may be configured tostrobe according to a pattern recognizable by the UAV during approach tothereby identify the base station.

In another aspect of the present disclosure, a UAV is disclosed thatincludes a power source. The power source includes: one or more powercells; one or more thermal transfer members that are thermally connectedto the one or more power cells; and a heat exchanger that is thermallyconnected to the one or more thermal transfer members such that the oneor more thermal transfer members and the heat exchanger facilitate atransfer of thermal energy between the power source and ambient air todecrease or increase temperature of the power source.

In certain embodiments, the one or more thermal transfer members mayextend between the one or more power cells and the heat exchanger.

In certain embodiments, the one or more thermal transfer members mayinclude graphite.

In certain embodiments, the one or more thermal transfer members may beunitary in construction.

In certain embodiments, the one or more power cells and the one or morethermal transfer members may correspond in number.

In certain embodiments, the one or more power cells may include aplurality of individual power cells and the one or more thermal transfermembers may include a plurality of individual thermal transfer members.

In certain embodiments, the heat exchanger may include one or morediffusers to increase surface area of the heat exchanger and thermalenergy distribution towards or away from the power source.

In certain embodiments, the one or more diffusers may extend axiallyand/or laterally along an outer surface of the heat exchanger.

In certain embodiments, the one or more diffusers may include aplurality of diffusers.

In certain embodiments, the plurality of diffusers may be configured asfins that define one or more channels therebetween.

In certain embodiments, the one or more channels may be configured todirect air flow along the heat exchanger to increase thermal energydistribution towards or away from the power source.

In another aspect of the present disclosure, a UAV is disclosed thatincludes a power source. The power source includes a heat exchanger thatis configured to transfer thermal energy between the power source andambient air to decrease or increase temperature of the power source. Theheat exchanger includes one or more diffusers to increase surface areaof the heat exchanger and thermal energy distribution towards or awayfrom the power source.

In certain embodiments, the one or more diffusers may extend axiallyand/or laterally along an outer surface of the heat exchanger.

In certain embodiments, the one or more diffusers may include aplurality of diffusers.

In certain embodiments, the plurality of diffusers may be configured asfins that define one or more channels therebetween.

In certain embodiments, the one or more channels may be configured todirect air flow along the heat exchanger to increase thermal energydistribution towards or away from the power source.

In another aspect of the present disclosure, a UAV is disclosed thatincludes: a body; one or more antennas that extend from the body; and apower source that is connected to the body. The one or more antennas arereconfigurable between an active configuration, in which the one or moreantennas extend outwardly from the body, and a passive configuration, inwhich the one or more antennas are positioned adjacent to the body. Thepower source includes one or more diffusers that extend axially and/orlaterally along an outer surface of the power source to transfer thermalenergy between the power source and ambient air to decrease or increasetemperature of the power source.

In certain embodiments, the one or more antennas may be biased towardsthe active configuration.

In certain embodiments, the one or more diffusers may include aplurality of diffusers.

In certain embodiments, the plurality of diffusers may be configured asfins that define one or more channels therebetween.

In certain embodiments, the one or more channels may be configured todirect air flow along the power source to increase thermal energydistribution towards or away from the power source.

In certain embodiments, the power source may further includes one ormore power cells and one or more thermal transfer members that arethermally connected to the one or more power cells and to the one ormore diffusers.

In certain embodiments, the one or more thermal transfer members mayinclude graphite.

In certain embodiments, the one or more thermal transfer members may beunitary in construction.

BRIEF DESCRIPTION OF THE DRAWINGS

The present disclosure is best understood from the following detaileddescription when read in conjunction with the accompanying drawings. Itis emphasized that, according to common practice, the various featuresof the drawings are not to-scale. On the contrary, the dimensions of thevarious features are arbitrarily expanded or reduced for clarity.

FIG. 1 is a front, perspective view of a base station (dock) accordingto the principles of the present disclosure.

FIG. 2 is a partial, side view of the base station shown with oneembodiment of a UAV docked within a cradle of the base station.

FIG. 3 is a partial, side view of the base station shown with analternate embodiment of the UAV seen in FIG. 2 .

FIG. 4 is a bottom, perspective view of a power source of the UAV.

FIG. 5 is a partial, side, perspective view of the power source of theUAV.

FIG. 6 is a side, schematic view of the base station.

FIG. 7 is a partial, rear, perspective view of the base station.

FIG. 8 is a partial, side, perspective view of the base stationillustrating a plurality of actuators that are configured to open andclose a door of the base station.

FIGS. 9 and 10 are partial, top, perspective views of the base stationillustrating the plurality of actuators.

FIG. 11 is a partial, front, perspective view of the base stationillustrating a cap that is supported on a slide mechanism, whichfacilitates movement of the cradle between a retracted position and anextended position.

FIG. 12 is a partial, rear, perspective view of the cap shown overlayedby the door of the base station upon closure.

FIG. 13 is a partial, side, perspective view of the base station withthe cradle shown in the extended position.

FIG. 14 is a partial, top, perspective view of the base stationillustrating one or more connection antennas and one or more fiducialsthat are supported on a roof section thereof.

FIG. 15 is a partial, top, perspective view of the base stationaccording to an embodiment of the disclosure that includes a pluralityof fiducials on the roof section.

FIG. 16 is a partial, front, perspective view of the base stationillustrating a status indicator.

FIG. 17 is a partial, top, perspective view of the base stationaccording to an embodiment of the disclosure that includes anillumination system on the roof section.

FIG. 18A is a partial, front, perspective view of the base stationduring movement of the cradle into the retracted position after dockingof the UAV.

FIG. 18B is a partial, front, perspective view of the base stationduring movement of the cradle into the retracted position after dockingof the UAV illustrating one embodiment of a contact member that isconfigured to facilitate reconfiguration (e.g., folding) of one or moreantennas on the UAV

FIGS. 19 and 20 are opposite side, schematic views of a temperaturecontrol system of the base station, which includes a first air circuit;a second air circuit; and a thermoelectric conditioner (TEC).

FIG. 21 is a partial, side, schematic view of the cradle and the secondair circuit.

FIG. 22 is partial, side, schematic view of the temperature controlsystem.

FIG. 23 is a partial, side, schematic view of the temperature controlsystem illustrating a first heat sink and a second heat sink.

FIG. 24 is a partial, side, schematic view of the first heat sink andthe second heat sink, which is shown located within a plenum of thesecond air circuit.

FIG. 25 is a partial, top, schematic view of the base station accordingto an embodiment of the disclosure that includes one or more heatingelements on the roof section.

FIG. 26 is a partial, top, schematic view of the base stationillustrating an internal fan.

FIG. 27 is a partial, rear, perspective view of the base stationillustrating one or more channels that collect and direct water.

DETAILED DESCRIPTION Overview

The present disclosure relates to a base station for use with a UAV thatis configured to not only charge the power source of the UAV, butregulate the temperature of the power source of the UAV. In variousembodiments of the disclosure, depending upon the environmentalconditions, the base station may be configured to cool the power sourceof the UAV (e.g., when the base station and the UAV are used in warmerenvironments) or heat the power source of the UAV (e.g., when the basestation and the UAV are used in cooler environments).

To facilitate cooling and/or heating of the power source of the UAV, thebase station includes a temperature control system. The temperaturecontrol system includes: a thermoelectric conditioner (TEC); a first aircircuit that is thermally connected to the TEC and which is configuredto regulate (e.g., increase or decrease) temperature of the TEC; and asecond air circuit that is thermally connected to the TEC such that theTEC is located between the first air circuit and the second air circuit.The second air circuit is configured to direct treated air (e.g., airthat has been either cooled or heated) across the power source of theUAV to thereby heat or cool the power source (subject to environmentalconditions).

To increase functionality and improve operation of the base station, thebase station includes a plurality of additional (ancillary) systems thatare configured to address environmental concerns (e.g., humidity,precipitation, etc.), security concerns (e.g., anti-theft systems andmechanisms), etc. For example, the base station may include: a heatingelement that is supported by a roof section to reduce the presence ofsnow and/or ice; at least one fiducial that facilitates visualidentification of the base station by the UAV; an illumination systemthat improves visibility of the at least one fiducial (e.g., duringnighttime operation); and a visualization system (e.g., a digital imagecapturing device) that supports observation and visual analysis of theenvironment in which the base station and the UAV are located.

Referring now to the drawings, FIGS. 1 and 2 illustrate an unmannedaerial vehicle (UAV) 10 and a base (docking) station 100 that isconfigured for automated servicing (e.g., docking, storage, charging,operation, etc.) and accommodation of the UAV 10. While a single UAV 10and a single base station 100 are shown and described herein, in certainembodiments of the disclosure, it is envisioned that a plurality of UAVs10 and a plurality of base stations 100 may be utilized depending, forexample, upon the particular intended use of the UAVs 10.

The UAV

The UAV 10 includes one or more propulsion mechanisms (systems) 12 and apower source 14 (e.g., a battery 16). To support autonomous landing anddocking of the UAV 10 with the base station 100, it is envisioned thatthe UAV 10 may follow any suitable process or procedure and may includeany suitable electrical and/or logic components, as described in U.S.application Ser. No. 16/991,122 (“the '122 application”), the entirecontents of which are hereby incorporated by reference.

The propulsion mechanism(s) 12 may include any components and/orstructures suitable for the intended purpose of supporting flight of theUAV 10. For example, as seen in FIG. 2 , it is envisioned that thepropulsion mechanism(s) 12 may include propellers 18. It should beappreciated, however, that the particular configuration and/orcomponents of the propulsion mechanism(s) 12 may be varied withoutdeparting from the scope of the present disclosure. FIG. 3 , forexample, illustrates an alternate configuration for the UAV 10.

Although shown as including four propulsion mechanisms 12 in theparticular embodiment of the UAV 10 described herein, it should beappreciated that the particular number of propulsion mechanisms 12 maybe varied without departing from the scope of the present disclosure. Assuch, embodiments of the UAV 10 including fewer and greater numbers ofpropulsion mechanisms 12 are also envisioned herein and are not beyondthe scope of the present disclosure.

It is envisioned that the propulsion mechanism(s) 12 may include eithera fixed configuration or a variable configuration. For example, it isenvisioned that the propulsion mechanism(s) 12 may be reconfigurablebetween an extended (first) configuration and a collapsed (folded,second) configuration to allow for a reduction in the overall size ofthe UAV 10 (e.g., during entry into the base station 100) and, thus, areduction in the overall size of the base station 100, as described infurther detail below.

The power source 14 is located (e.g., attached to or otherwise supportedon) a lower (bottom) surface of the UAV 10 and includes one or moreconducting (electrical) contacts (not shown) that are configured forengagement (contract) with one or more corresponding conducting(electrical) contacts on the base station 100 to enable charging of thepower source 14.

Heat Exchange

As seen in FIGS. 4 and 5 , the power source 14 includes one or morepower cells 20; one or more thermal transfer members 22; and a heatexchanger 24, which defines a lower (bottom) surface of the power source14 and acts as a cover for the power cell(s) 20 and the thermal transfermember(s) 22. The thermal transfer member(s) 22 and the heat exchanger24 are configured to facilitate the transfer of thermal energy betweenthe power source 14 and the ambient (air) to decrease or increasetemperature of the power source 14. For example, depending upon theparticular environment in which the UAV 10 and the base station 100 areemployed, the thermal transfer member(s) 22 and the heat exchanger 24may be utilized to dissipate heat generated by the power source 14during use and/or charging of the UAV 10 (e.g., in warmer environments)or to transfer heat to the power source 14 (e.g., in coolerenvironments) to thereby improve efficiency, operation, and/or theusable life of the UAV 10 and/or the power source 14.

In the particular embodiment illustrated, the power source 14 includes aplurality of individual (e.g., discrete) power cells 20. It should beappreciated, however, that the particular number and/or configuration ofthe power cells 20 may be varied in alternate embodiments withoutdeparting from the scope of the present disclosure. For example,embodiments of the power source 14 including a single power cell 20 arealso envisioned herein.

The thermal transfer member(s) 22 are thermally connected to, and extendbetween, the power cell(s) 20 and the heat exchanger 24. In theparticular embodiment of the disclosure illustrated, the power source 14includes a plurality of individual (e.g., discrete) thermal transfermembers 22, each of which is associated with (e.g., thermally connectedto) a corresponding power cell 20 (e.g., such that the power source 14includes a corresponding (equal) number of power cells 20 and thermaltransfer members 22). It should be appreciated, however, that theparticular number of the thermal transfer members 22 may be varied inalternate embodiments without departing from the scope of the presentdisclosure and that embodiments of the power source 14 including anunequal number of power cells 20 and thermal transfer members 22 arealso envisioned herein. For example, the present disclosure contemplatesembodiments in which the number of power cells 20 may exceed the numberof thermal transfer members 22 are also envisioned herein (e.g.,embodiments in which the power source 14 includes a single thermaltransfer member 22 that extends between the collection of power cells 20and the heat exchanger 24) as well as embodiments in which the number ofthermal transfer members 22 may exceed the number of power cells 20.

The thermal transfer member(s) 22 may include (e.g., may be formedpartially or entirely from) any material or combination of materialsthat is suitable for the intended purpose of transferring heat between,and thermally connecting, the power cell(s) 20 and the heat exchanger24. For example, in one particular embodiment, it is envisioned that thethermal transfer member(s) 22 may include (e.g., may be formed partiallyor entirely from) graphite. It should be appreciated, however, that theuse of other materials would not be beyond the scope of the presentdisclosure. Additionally, although each thermal transfer member 22 isshown as being unitary in construction (i.e., as being formed from asingle piece of material), in alternate embodiments of the disclosure,it is envisioned that each thermal transfer member 22 may include aseries of individual segments that are connected to each other duringmanufacture, assembly of the power source 14, or at any other suitablepoint in time.

The heat exchanger 24 is thermally connected to the thermal transfermember(s) 22 and is configured to communicate and distribute thermalenergy between the power source 14 and the ambient (air), either awayfrom the power source 14 (e.g., when utilized in warmer environments) ortowards the power source 14 (e.g., when utilized in coolerenvironments), and may include (e.g., may be formed partially orentirely from) any material or combination of materials suitable forthat intended purpose. For example, it is envisioned that the heatexchanger 24 may include (e.g., may be formed partially or entirelyfrom) aluminum, magnesium, copper, etc.

To increase the available surface area and, thus, the distribution ofthermal energy (either towards or away from the power source 14), incertain embodiments, such as that illustrated throughout the figures,the heat exchanger 24 may include one or more diffusers 26, which may beconfigured in any manner suitable for that intended purpose. Forexample, it is envisioned that the diffuser(s) 26 may be configured aspins, protrusions, ribs, or other such surface irregularities and mayextend axially (e.g., along a longitudinal axis Y) and/or laterally(e.g., a long a transverse axis X) along an outer (bottom) surface 28 ofthe heat exchanger 24. In the particular embodiment of the heatexchanger 24 illustrated throughout the figures, for example, thediffusers 26 are configured as fins 30 that define a plurality ofchannels 32 therebetween, which collectively direct air flow along theheat exchanger 24 to further increase the distribution of thermalenergy.

Although shown as including a plurality of diffusers 26 and channels 32in the particular embodiment of the disclosure illustrated, it should beappreciated that the particular number of the diffusers 26 and/orchannels 32 may be varied in alternate embodiments without departingfrom the scope of the present disclosure. For example, embodiments ofthe heat exchanger 24 including a single diffuser 26 are also envisionedherein.

Base Station Construction

With reference now to FIGS. 4-13 as well, the base station 100 includes:an enclosure (body) 102; a door 104 that is movably connected to theenclosure 102; and a cradle 106 that is configured to receive(accommodate) the UAV 10.

The enclosure 102 includes an inner housing (shell) 108 and an outerhousing (cover) 110. The respective inner and outer housings 108, 110are configured as separate, discrete structures that may be connectedtogether in any suitable manner, whether fixedly or removably (e.g., toallow for repeated assembly and disassembly of the base station 100during maintenance, repair, etc.). For example, it is envisioned thatthe respective inner and outer housings 108, 110 may be connected via aplurality of mechanical fasteners (e.g., screws, pins, bolts, clips,etc.), which may be hidden (or otherwise obscured) to inhibit theftand/or unauthorized disassembly of the base station 100.

The inner housing 108 defines an internal cavity 112 that is configuredto receive and accommodate the UAV 10. Additionally, the inner housing108 provides a mounting surface for various components of the basestation 100 including, for example, electrical components, actuators,and the like, which are secured (mounted) to the inner housing 108 andsupport operation of the base station 100.

The outer housing 110 provides structural support to the base station100 and protects the inner housing 108 and the various components thatare secured (mounted) thereto (e.g., from dust, debris, the ingress ofmoisture and/or water, etc.). Additionally, the outer housing 110supports various external components of the base station 100, asdescribed in further detail below.

To facilitate access to the various components accommodated within theouter housing 110 (and/or the inner housing 108), in certainembodiments, it is envisioned that the outer housing 110 may include anaccess panel 114 (FIG. 7 ) to support maintenance, repair, etc., whichmay be incorporated in any suitable location (e.g., at a rear of theouter housing 110). To inhibit theft and/or unauthorized access, it isenvisioned that the access panel 114 may include a locking mechanism orother such suitable safeguard.

In certain embodiments of the disclosure, it is envisioned that theouter housing 110 may include exterior coloration that not only reducessolar loading (heating), but promotes contrast to facilitatevisualization and/or identification of the base station 100 by the UAV10 during docking, as described in further detail below.

The door 104 is movably connected to the outer housing 110 such that thedoor 104 is repositionable between a closed position (FIG. 1 ), in whichthe door 104 conceals the internal cavity 112, and an open position(FIG. 6 ), in which the internal cavity 112 is exposed. Morespecifically, the door 104 is movably connected to a forward frame 116of the outer housing 110. Although illustrated as being pivotablyconnected to the forward frame 116 in the particular embodimentillustrated throughout the figures, it is also envisioned that the door104 may be slidably repositionable between the closed position and theopen position in alternate embodiments of the disclosure.

To facilitate movement of the door 104 between the closed position andthe open position, the base station 100 includes one or more actuators118 (FIGS. 8-10 ) that extend between the door 104 and the enclosure102. Although shown as including a plurality (e.g., two) actuators 118in the particular embodiment illustrated, which are secured to opposinglateral ends of the door 104, it should be appreciated that the presentdisclosure also contemplates embodiments in which a single actuator 118may be utilized to control the position of the door 104 (e.g., to reducethe overall cost and complexity of the base station 100).

Each actuator 118 includes a motor assembly 120 (e.g., a stepper motor)and a linkage assembly 122 that extends between the motor assembly 120and the door 104. More specifically, each motor assembly 120 is securedto the inner housing 108 such that the motor assembly(ies) 120 arelocated between the inner housing 108 and the outer housing 110, whichprotects the motor assembly(ies) 120 and inhibits the collection of anydust, debris, etc. The linkage assembly 122 extends from the motorassembly 120, through the inner housing 108, and pivotably engages thedoor 104 such that, upon actuation of the motor assembly 120, thelinkage assembly 122 applies a force to the door 104 to therebyfacilitate movement of the door 104 between the closed position and theopen position.

Each linkage assembly 122 includes: a (threaded) drive screw 124; acarrier 126; a first arm 128; and a second arm 130. The drive screw 124is (operatively) connected to the motor assembly 120 such that actuationof the motor assembly 120 causes rotation of the drive screw 124. Thecarrier 126 is threadably engaged to the drive screw 124 such thatrotation of the drive screw 124 causes axial translation of the carrier126. More specifically, rotation of the drive screw in a first direction(e.g., clockwise) causes forward advancement of the carrier 126 (e.g.,movement of the carrier 126 towards the door 104) and rotation of thedrive screw in a second direction (e.g., counterclockwise) causesrearward advancement of the carrier 126 (e.g., movement of the carrier126 away from the door 104). The first arm 128 includes a first end 132that is connected to the carrier 126 (either fixedly or pivotably) and asecond end 134 that is pivotably connected to the second arm 130. Thesecond arm 130 includes a first end 136 that is pivotably connected tothe second end 134 of the first arm 128 and a second end 138 that ispivotably connected to a bracket 140. The bracket 140 is fixedlyconnected to the door 104 which allows for the transmission of forcefrom the carrier 126 to the door 104 via the arms 128, 130.

The cradle 106 is configured for electrical connection to the powersource 14 of the UAV 10 during docking to facilitate (support) chargingof the power source 14. More specifically, the cradle 106 defines achamber 142 (FIG. 10 ) that is configured to receive the power source 14and an electrical contact 144 that is configured for engagement with oneor more corresponding electrical contacts on the power source 14. Todirect the UAV 10 during docking and facilitate a proper electricalinterface between the power source 14 and the cradle 106, the cradle 106defines sidewalls 146 that taper inwardly towards the chamber 142 so asto defines a guide surface 148, as seen in FIG. 10 .

The cradle 106 is movable between a retracted position (FIGS. 2, 10 ),in which the cradle 106 is positioned within the enclosure 102 (e.g.,within the internal cavity 112), an extended position (FIG. 13 ), inwhich the cradle 106 is positioned externally of the enclosure 102 tofacilitate docking with the UAV 10. To support movement between theextended and retracted positions, the cradle 106 is connected to atelescoping slide mechanism 150 that extends through a window 152 (FIG.1 ) defined by a bezel portion 154 of the forward frame 116. The slidemechanism 150 supports a cap (hatch, cover) 156 (FIG. 11 ) that isconfigured in correspondence with the window 152 such that, uponmovement of the cradle 106 into the retracted position, the cap 156engages the bezel portion 154 and is received within the window 152.

In certain embodiments of the disclosure, such as that illustratedthroughout the figures, the cap 156 may include an upstanding tab 158(FIG. 11 ) that is configured for receipt within a corresponding recess160 (FIGS. 8, 12 ) defined in an inner surface 162 of the door 104.Receipt of the tab 158 within the recess 160 not only allows for properclosure of the door 104, but allows for overlayment of the cap 156 bythe door 104 upon closure to facilitate sealing of the enclosure 102 andinhibit (if not entirely prevent) the entry of dust, debris, etc.,through the door 104 and/or the bezel portion 154. Additionally, theengagement between the bezel portion 154, the slide mechanism 150, andthe door 104 (e.g., reception of the tab 158 by the recess 160) improvesthe security of the base station 100 by inhibiting access to the cradle106 and, thus, the UAV 10.

In certain embodiments of the disclosure, it is envisioned that the door104 and the cradle 106 may be automatically actuated upon the receipt ofan incoming/docking signal from the UAV 10. For example, it isenvisioned that the incoming/docking signal may automatically engage theactuator(s) 118 to thereby open the door 104. Thereafter, when it isdetermined that the door 104 is fully opened, which may be achievedthrough the employ of Hall sensors (or any other such suitable detectionmechanism), the cradle 106 may be extended via (telescopic) movement ofthe slide mechanism 150.

Anti-Theft and Security Measures

To further improve the security of the base station 100, in certainembodiments of the disclosure, it is envisioned that the door 104 mayinclude a locking mechanism. For example, it is envisioned that the door104 may include a magnetic lock to maintain closure of the door 104 inthe absence of power to prevent inadvertent and/or unauthorized openingof the door 104 and, thus, access to the UAV 10.

Additionally, or alternatively, it is envisioned that the actuator(s)118 (FIGS. 8-10 ) may be configured to resist the application of(manual) force to the door 104, and thereby maintain closure of the door104, by inhibit (if not entirely preventing) the transmission of forcefrom the door 104 to the motor assembly(ies) 120. For example, it isenvisioned that the threading defined by the drive screw 124 may includea fine pitch, which would inhibit (if not entirely prevent) thetransmission of force applied to the door 104 to the carrier(s) 126,thereby maintaining closure of the door 104. Additionally, oralternatively, it is envisioned that the actuator(s) 118 may include asolenoid (or other such mechanism) that is configured to engage alocking pin (or other such member).

Pedestal

With reference to FIG. 1 , in certain embodiments, the base station 100may be configured for use with a pedestal 164 (or other suchfree-standing platform or support) to elevate the base station 100 andthe UAV 10. Elevation of the base station 100 and the UAV 10 createsfree air space that not only reduces turbulence (e.g., propeller wash)during takeoff and landing of the UAV 10, but mitigates the entry ofdebris (e.g., dust, particulate, etc.) into the base station 100.

It is envisioned that the pedestal 164 and the base station 100 mayinclude corresponding engagement structures (e.g., pins and holes,detents and recesses, ribs and slots, a footing and a channel, etc.)that are configured for releasable engagement (connection) to promoteproper alignment of the pedestal 164 and the base station 100 andinhibit (if not entirely prevent) unintended separation of the basestation 100 from the pedestal 164, such as, for example, in the eventthat the base station 100 and/or the pedestal 164 is subjected to anapplied force (e.g., a wind gust, impact with an external object, etc.).In one particular embodiment, it is envisioned that the correspondingengagement structures may include one or more openings and correspondingmechanical fasteners (e.g., bolts, screws, pins, etc.) that areconfigured for insertion into the opening(s) to allow for fixed,releasably connection of the pedestal 164 and the base station 100.

To inhibit (if not entirely prevent) unauthorized separation of the basestation 100 from the pedestal 164 (e.g., to guard against theft of thebase station 100 and/or the pedestal 164), it is envisioned that thepedestal 164 and the base station 100 may include corresponding eyelets(or other such openings) that are configured to receive a lockabletether, chain, cable, bar, etc.

Takeoff Landing, and Docking

With reference now to FIGS. 14-18 as well, the base station 100 includesa plurality of systems, components, and features that support takeoff ofthe UAV 10, landing of the UAV 10, and docking of the UAV 10. Forexample, as described below, the base station 100 may include: one ormore connection antennas 166; one or more fiducials 168 that aresupported by the enclosure 102; an illumination system 170 that issupported by the enclosure 102; one or more status indicators 172 thatare supported by the enclosure 102; and a visualization system 174 thatis supported by the enclosure 102.

Connection Antennas

The base station 100 includes primary connection antenna(s) 166 thatfacilitate wireless communication between the base station 100 and theUAV 10, either directly or indirectly. For example, it is envisionedthat that the primary connection antenna(s) 166 may be utilized tofacilitate communication between the base station 100 and an interveningcommunication point, such as a hangar, a warehouse, etc. In suchembodiments, the primary connection antenna(s) 166 on the base station100 support direct communication with the hangar (or the like), whichwould communicate directly with the UAV 10.

In the particular embodiment seen in FIG. 14 , for example, the basestation 100 includes a pair of primary connection antennas 166 that aresecured to (or otherwise engaged with) a roof section 176 of the outerhousing 110. It should be appreciated, however, that the particularnumber of primary connection antennas 166 and/or the location of theprimary connection antennas 166 may be varied in alternate embodimentswithout departing from the scope of the present disclosure. For example,embodiments including a single primary connection antenna 166 are alsoenvisioned herein, as are embodiments in which the base station 100 mayinclude one or more primary connection antennas 166 that are located onsidewalls of the outer housing 110.

In certain embodiments of the disclosure, it is envisioned that the basestation 100 may include one more secondary communication antennas thatfacilitate communication over cellular and/or WiFi networks and/orsupport GPS functionality. In such embodiments, it is envisioned thatthe primary connection antenna(s) 166 and the secondary communicationantenna(s) may operate in tandem. For example, embodiments areenvisioned in which the primary communication antenna(s) 166 mayfacilitate docking of the UAV 10 with the base station 100 (andcommunication therebetween) while the secondary communication antenna(s)may facilitate communication between the base station 100 and the hangar(or vice versa).

Fiducials

The fiducials 168 facilitate not only visual identification of the basestation 100 by the UAV 10, but guidance of the UAV 10 during landing anddocking with the base station 100. To promote or otherwise enhancevisualization and/or recognition of the fiducials 168, it is envisionedthat the outer housing 110 may include contrasting coloration.

In the particular embodiment of the disclosure seen in FIGS. 13-15 , forexample, the base station 100 includes (first and second) fiducials 168i, 168 ii that are located on (supported by) the roof section 176 of theouter housing 110 (e.g., between the primary connection antennas 166)and a (third) fiducial 168 iii that is associated with (e.g., located onor adjacent to) the cradle 106. It should be appreciated, however, thatthe particular number of fiducials 168 and/or the location(s) thereof,may be varied in alternate embodiments without departing from the scopeof the present disclosure.

The fiducial 168 i is initially recognized by the UAV 10 to guide theUAV 10 during approach. The fiducial 168 i defines a (first) surfacearea, which is sufficiently large to allow for visual recognition by theUAV 10 from a desired distance. For example, in certain embodiments, itis envisioned that the (first) surface area defined by the fiducial 168i may lie substantially within the range of (approximately) 40 percentto (approximately) 80 percent of the surface area defined by the roofsection 176. Surface areas for the fiducial 168 i that lie outside thedisclosed range, however, would not be beyond the scope of the presentdisclosure (e.g., to account for advancements in visualizationtechnology utilized in the UAV 10).

The fiducial 168 ii is configured as an identification member 178 thatis recognized by the UAV 10 during approach to the base station 100(e.g., after recognition of the fiducial 168 i), which allows the UAV 10to distinguish amongst a plurality of base stations 100 to facilitateproper pairing (e.g., docking of the UAV 10 to a specific base station100). In certain embodiments of the disclosure, it is envisioned thatthe fiducial 168 i may be fixedly connected to the base station 100(e.g., the roof section 176) and that the fiducial 168 ii may beconfigured for removable connection to the base station 100 (e.g., theroof section 176). Removable connection of the fiducial 168 ii allowsfor the uniform manufacture of a fleet of base stations 100 and thesubsequent attachment of the fiducials 168 ii thereto. Embodiments inwhich the fiducial 168 ii may be integrally (e.g., monolithically)formed with the base station 100, however, would not be beyond thepresent disclosure.

In the particular embodiment illustrated, the fiducial 168 ii defines a(second) surface area, which is less than the (first) surface areadefined by the fiducial 168 i. For example, it is envisioned that the(second) surface area defined by the fiducial 168 ii may liesubstantially within the range of (approximately) 10 percent to(approximately) 50 percent of the (first) surface area defined by thefiducial 168 i. Surface areas for the fiducial 168 ii that lie outsidethe disclosed range, however, would not be beyond the scope of thepresent disclosure (e.g., to account for advancements in visualizationtechnology utilized in the UAV 10).

The fiducial 168 iii is configured as an April tag 180 and is recognizedby the UAV 10 after recognition of the fiducial 168 ii. In theparticular embodiment of the disclosure illustrated, the fiducial 168iii is located on the slide mechanism 150, which inhibits (if notentirely prevents) any interference with air flow across the cradle 106during cooling and/or heating of the power source 14 of the UAV 10,which is discussed in further detail below. Embodiments in which thefiducial 168 iii may be located on the cradle 106 itself, however, arealso envisioned herein and would not be beyond the scope of the presentdisclosure.

Illumination System

The illumination system 170 is configured to improve visibility of thefiducials 168 during nighttime operation. In the particular embodimentof the disclosure illustrated, the illumination system 170 includes oneor more light sources 182 (FIG. 15 ) (e.g., LEDs 184) that are secured,mounted to, or otherwise supported by the roof section 176 of the outerhousing 110 to support lighting (illumination) of the fiducials 168 i,168 ii. It is envisioned that the illumination system 170 may beconnected to any suitable power source, whether internal to the basestation 100 (e.g., to the power supply controlled by the mainboard/processor) or external (e.g., to a separate power supply, battery,or the like).

In certain embodiments of the disclosure, it is envisioned that theillumination system 170 may be controlled by the main board/processorand configured to flash or strobe the light source(s) 182 according to aparticular pattern, which can be recognized by the UAV 10 duringapproach to thereby identify the base station 100. In such embodiments,it is envisioned that the illumination system 170 may either supplementor replace the fiducial 168 ii as a means of identifying the basestation 100.

Status Indicators

The status indicator(s) 172 (FIG. 16 ) identify the status of the basestation 100 (e.g., that the base station 100 is ready, requires service,is undergoing the docking procedure with the UAV 10, etc.). In certainembodiments, it is envisioned that the status indicator(s) 172 mayinclude a series of LEDs 186, which not only supports status indication,but illumination of the fiducial 168 iii (FIG. 13 ) and/or the cradle106 (e.g., to facilitate docking of the UAV 10). For example, in oneparticular embodiment, it is envisioned that one or more of the LEDs 186may be configured to emit a colored light (e.g., red, blue, yellow,etc.) and that one or more of the LEDs 186 may be configured to emit awhile light to illuminate the fiducial 168 iii and/or the cradle 106.

In the particular embodiment of the disclosure illustrated in FIG. 16 ,the status indicator(s) 172 are secured, mounted to, or otherwisesupported by the forward frame 116 of the outer housing 110. It shouldbe appreciated, however, that the particular location of the statusindicator(s) 172 may be varied in alternate embodiments withoutdeparting from the scope of the present disclosure. It is envisionedthat the status indicator(s) 172 may be connected to any suitable powersource, whether internal to the base station 100 (e.g., to the powersupply controlled by the main board/processor) or external (e.g., to aseparate power supply, battery, or the like).

UAV Storage

In certain embodiments of the disclosure, it is envisioned that thepropulsion mechanism(s) 12 (FIG. 2 ) (e.g., the propellers 18) of theUAV 10 may be reconfigurable between unfolded (flight) and folded(storage) configurations, which allows for a reduction in the overallsize of the base station 100. To support movement from the unfoldedconfiguration to the folded configuration, it is envisioned that thebase station 100 may be configured for engagement with the of thepropulsion mechanism(s) 12 (e.g., during retraction of the cradle 106).For example, it is envisioned that the base station 100 may include oneor more engagement members that are configured to physically interfacewith the propulsion mechanism(s) 12 to move the propulsion mechanism(s)12 into the folded configuration. It is envisioned that the engagementmember(s) may be integrated into (or defined by) one or more surface(s)of the enclosure 102 (e.g., the forward frame 116 of the outer housing110). For example, the engagement member(s) may be configured asrollers, brushes, or the like.

In certain embodiments of the disclosure, it is envisioned that theengagement member(s) may be configured for passive interaction with thepropulsion mechanism(s) 12, whereby the propulsion mechanism(s) 12 arebrought into contact with the engagement member(s) by virtue of theretraction of the cradle 106. Alternatively, it is envisioned that theengagement member(s) may be configured for active engagement(interaction) with the propulsion mechanism(s) 12. For example, it isenvisioned that the engagement member(s) may be repositionable(reconfigurable) between a first position (configuration), in which theengagement member(s) are positioned (configured) to avoid contact withthe propulsion mechanism(s) 12 (e.g., such that the engagement member(s)are located outside the path followed by the propulsion mechanism(s) 12during retraction of the cradle 106), and a second position(configuration), in which the engagement member(s) are positioned(configured) for contact with the propulsion mechanism(s) 12 (e.g., suchthat the engagement member(s) are located within the path followed bythe propulsion mechanism(s) 12 during retraction of the cradle 106).

To allow for additional reductions in the overall size of the basestation 100, it is envisioned that the base station 100 may include oneor more contact members 188 that are configured for engagement (contact)with one or more antennas 34 on the UAV 10 to facilitate reconfiguration(repositioning, folding) thereof between an active (use, unfolded,deployed) configuration (FIG. 2 ), in which the antenna(s) 34 extendoutwardly (away) from a body 36 of the UAV 10, which supports (isconnected to) the power source 14, and a passive (storage, folded,undeployed) configuration, in which the antenna(s) 34 are positionedadjacent to (e.g., in contact (engagement) with the body 36 of the UAV10). Reconfiguration of the antenna(s) 34 from the active configurationinto the passive configuration creates clearance with the internalcomponents of the base station 100 to inhibit (if not entirely prevent)unintended contact between the UAV 10 and the base station 100 duringmovement of the cradle 106 (and the UAV 10) between the extendedposition (FIG. 13 ) and the retracted position (FIGS. 2, 10 ). In theparticular embodiment of the UAV 10 illustrated throughout the figures,the antenna(s) 34 are biased towards the active configuration via one ormore biasing members (e.g., springs or the like) such that theantenna(s) 34 are automatically reconfigured from the passiveconfiguration into the active configuration as the UAV 10 exits the basestation 100 (e.g., via movement of the cradle 106 from the retractedposition (FIGS. 2, 10 ) into the extended position (FIG. 13 )).

In the embodiment illustrated in FIG. 18A, the contact member 188defines a groove (channel) 189 that is configured to receive theantenna(s) 34 during retraction of the cradle 106 as the UAV 10 iswithdrawn into the enclosure 102. FIG. 18B illustrates anotherembodiment of the contact member 188 that includes a leading (forward)edge 190 and a trailing (rear) edge 192 and defines a (vertical) heightH that varies between the edges 190, 192 so as to defined an angled(chamfered, beveled) surface 194 that is configured for engagement(contact) with the antenna(s) 34 on the UAV 10. In the particularembodiment of the disclosure seen in FIG. 18B, each contact member 188tapers such that the height H decreases from the leading edge 190towards the trailing edge 192. Embodiments in which each contact member188 may taper such that the height H increases from the leading edge 190towards the trailing edge 192 are also envisioned herein and would notbe beyond the scope of the present disclosure (e.g., depending upon theparticular configuration and/or location of the antenna(s) on the UAV10, spatial constraints of the enclosure 102, etc.).

In the embodiments illustrated in FIGS. 18A and 18B, the base station100 includes a single contact member 188 that is secured to (orotherwise engaged with) an inner (e.g., upper) surface 196 of the innerhousing 108. It should be appreciated, however, that the particularnumber of contact members 188 and/or the location of the contactmember(s) 188 may be varied in alternate embodiments without departingfrom the scope of the present disclosure (e.g., depending upon thenumber of antennas 34 on the UAV 10 and/or the location thereof). Forexample, embodiments including multiple contact members 188 are alsoenvisioned herein, as are embodiments in which the base station 100 mayinclude one or more contact members 188 that are located on sidewalls198 of the inner housing 108.

It is envisioned that the contact member(s) 188 may be secured to theinner housing 108 in any suitable manner. For example, it is envisionedthat the contact member(s) 188 may be integrally (e.g., monolithically)formed with the inner housing 108 or that the contact member(s) 188 andthe inner housing 108 may be formed as separate, discrete structures,which may be secured together via one or more mechanical fasteners, anadhesive, etc.

Temperature Control System

With reference now to FIGS. 19-24 , the base station 100 includes atemperature control (e.g., heating and cooling) system 200 that isconnected to the cradle 106 and is configured to vary (regulate) thetemperature of the power source 14 (FIGS. 2, 4, 5 ) when the UAV 10 isdocked in the base station 100 (e.g., cool or heat the UAV 10 subject toenvironmental conditions). In the particular embodiment of thedisclosure illustrated throughout the figures, the temperature controlsystem 200 is configured to cool the power source 14 of the UAV 10(e.g., when the UAV 10 and the base station 100 are operated in warmerenvironments). It should be appreciated, however, that embodiments inwhich the temperature control system 200 may be configured to heat thepower source 14 of the UAV 10 (e.g., when the UAV 10 and the basestation 100 are operated in cooler environments) are also envisionedherein and would not be beyond the scope of the present disclosure, asdescribed in further detail below.

The temperature control system 200 includes: an upper air circuit 202; alower air circuit 204; and a thermoelectric conditioner (TEC) 206 thatis thermally connected to, and located between, the respective upper andlower air circuits 202, 204.

The upper air circuit 202 is an open system that receives and circulatesambient air, which may be sourced from within the base station 100 orexternally of the base station 100 (e.g., via an air intake) to vary(regulate) the temperature of the TEC 206. The upper air circuit 202includes: an upper (first) plenum 208; an upper (first) air circulator210; and an upper (first) heat sink 212.

The upper plenum 208 includes an (upper) ducting system 214 thatreceives and circulates the ambient air. The ducting system 214 mayinclude any suitable material (or combination of materials) and mayinclude either a unitary configuration, in which the upper plenum 208 isformed from a single piece of material, or a segmented configuration, inwhich the upper plenum 208 is formed from a plurality of segments thatare connected together (e.g., via one or more mechanical fasteners, anadhesive, in an interference fit, etc.).

The upper air circulator 210 supports and directs air flow through theupper plenum 208 and across the upper heat sink 212 to vary airtemperature within the upper air 202 and thereby regulate thetemperature of the TEC 206, as described in further detail below. Theupper air circulator 210 may include any structure or mechanism suitablefor that intended purpose and may be positioned in any locationsuitable. For example, in the illustrated embodiment, the upper aircirculator 210 is configured as a fan 216 that is located within theupper plenum 208 (e.g., within the ducting system 214). It is alsoenvisioned, however, that the upper air circulator 210 may be locatedexternally of the upper plenum 208. For example, the upper aircirculator 210 may be connected to (or otherwise supported on) anexterior surface 218 of the ducting system 214.

The upper heat sink 212 (FIGS. 23, 24 ) is connected to (e.g., locatedwithin) the upper plenum 208 and is configured to alter the temperatureof the air circulated through the upper air circuit 202. For example,when the temperature control system 200 is utilized to cool the powersource 14 (FIGS. 2, 4, 5 ) of the UAV 10, the upper heat sink 212absorbs and distributes thermal energy (heat) generated by the TEC 206to lower the temperature of the air flowing through the upper plenum208, as described in further detail below. To increase the absorptionand distribution of thermal energy by the upper heat sink 212, air flowthrough the upper plenum 208 and, thus, air flow across the upper heatsink 212, may be increased by increasing the speed of the upper aircirculator 210 (e.g., by increasing power to the fan 216).

The lower air circuit 204 includes a lower (second) plenum 220; a lower(second) air circulator 222; and a lower (second) heat sink 224 and isconfigured as a closed system. As such, in contrast to the upper aircircuit 202, rather than drawing in additional ambient air, the lowerair circuit 204 continuously circulates the air that is naturallypresent within the lower plenum 220.

The lower plenum 220 includes a (lower) ducting system 226 that directsair flow across the cradle 106 and the power source 14 of the UAV 10when the UAV 10 is docked within the base station 100 and may includeany suitable material (or combination of materials). The lower plenum220 (e.g., the ducting system 226) includes a segmented (non-unitary)configuration that defines a rear (first, fixed) section 228 and aforward (second, movable) section 230 that is movable in relation to therear section 228. The rear section 228 of the lower plenum 220 isfixedly connected (secured) to the TEC 206 and, as such, is fixed inrelation to the upper air circuit 202. The forward section 230 of thelower plenum 220 is connected (secured) to the cradle 106 and is movabletherewith during repositioning of the cradle 106 between the retractedposition (FIGS. 2, 10 ) and the extended position (FIG. 13 ). Theforward section 230 of the lower plenum 220 receives air from the rearsection 228 and defines an air inlet 232 and an air outlet 234. The airinlet 232 and the air outlet 234 each include one or more slits (orother such openings) that extend through the cradle 106 (e.g., thesidewalls 146) and into the chamber 142, which allows for air cooled bythe lower air circuit 204 to be directed into the chamber 142 and acrossthe power source 14 of the UAV 10 when the UAV 10 is docked in the basestation 100. More specifically, the air inlet 232 is configured todirect air into the cradle 106 and across the power source 14 of the UAV10 and the air outlet 234 is configured to receive the air directedacross the power source 14 and redirect the air through the lower plenum220 and across the lower heat sink 224, as described in further detailbelow.

Although shown as extending entirely about the cradle 106 in theparticular embodiment illustrated throughout the figures, embodimentsare also envisioned in which the forward section 230 of the lower plenum220 may only partially circumscribe the cradle 106. For example,embodiments are envisioned in which the forward section 230 of the lowerplenum 220 may include opposite terminal ends that respectively definethe air inlet 232 and the air outlet 234.

Additionally, while the forward section 230 of the lower plenum 220 andthe cradle 106 are illustrated as being integrally (e.g.,monolithically) formed in the illustrated embodiment, it is alsoenvisioned that the lower plenum 220 and the cradle 106 may beconfigured for releasable (detachable) engagement to allow for repeatedconnection and disconnection of the lower plenum 220 and the cradle 106(e.g., via corresponding engagement structures such as detents, clips,fasteners, or the like).

The lower air circulator 222 supports and directs air flow through thelower plenum 220 and across the lower heat sink 224 to thermallycondition the air within the lower air circuit 204 (e.g., vary thetemperature thereof) and thereby heat or cool the power source 14 of theUAV 10, as described in further detail below. The lower air circulator222 may include any structure or mechanism suitable for that intendedpurpose and may be positioned in any location suitable. For example, inthe illustrated embodiment, the lower air circulator 222 is configuredas a fan 236 that is located within the lower plenum 220 (e.g., withinthe ducting system 226). It is also envisioned, however, that the lowerair circulator 222 may be located externally of the lower plenum 220.For example, the lower air circulator 222 may be connected to (orotherwise supported on) an exterior surface 238 of the ducting system226.

The lower heat sink 224 is connected to (e.g., located within) the lowerplenum 220 and is configured to treat the air circulated therethrough(e.g., alter the temperature of the air within the lower plenum 220 viacooling or heating) prior to direction across the power source 14 of theUAV 10. For example, when the temperature control system 200 is utilizedto cool the power source 14 of the UAV 10, the lower heat sink 224absorbs and distributes thermal energy (heat) from the air flowingthrough the lower plenum 220 to lower the temperature thereof and, thus,the power source 14 of the UAV 10. To increase the absorption anddistribution of thermal energy by the lower heat sink 224 and, thus,enhance cooling of the power source 14 of the UAV 10, air flow throughthe lower plenum 220 and, thus, air flow across the lower heat sink 224,may be increased by increasing the speed of the lower air circulator 222(e.g., by increasing power to the fan 236).

The TEC 206 is configured as a Peltier system and includes and adedicated/integrated power source/control as well as a first (upper,“hot”) end 240 (FIG. 23 ) and a second (lower, “cold”) end 242, each ofwhich includes a thermal member (e.g., a ceramic plate). The first end240 is thermally and/or physically connected to the upper heat sink 212and the second end 242 is thermally and/or physically connected to thelower heat sink 224. Upon activation, as current flows through the TEC206, the temperature of the first end 240 increases (to an uppertemperature threshold) while the temperature of the second end 242decreases (to a lower temperature threshold) until a predetermined,fixed temperature differential is realized. For example, it isenvisioned that the differential between the respective upper and lowerends 240, 242 of the TEC 206 may lie substantially within the range of(approximately) 30° C. to (approximately) 70° C. (e.g., (approximately)50° C.). Embodiments in which the temperature differential may lieoutside the disclosed range, however, are also envisioned herein andwould not be beyond the scope of the present disclosure. Consequently,reducing the upper temperature threshold allows for a correspondingreduction in the lower temperature threshold.

During operation of the temperature control system 200, in theparticular embodiment of the disclosure illustrated, thermal energy(heat) generated by the TEC 206 is absorbed and dissipated by the upperheat sink 212 and the ambient air flowing through the upper plenum 208.The upper air circuit 202 thus cools the first (“hot”) end 240 of theTEC 206, which results in corresponding cooling of the second (“cold”)end 242 of the TEC 206 and, thus, increased cooling of the air flowingthrough the lower plenum 220 and the power source 14 of the UAV 10 whenthe UAV 10 is docked in the base station 100.

Although illustrated as including a single TEC 206 in the particularembodiment shown throughout the figures, embodiments are also envisionedin which the temperature control system 200 may include multiple TECs206. In such embodiments, it is envisioned that the TECs 206 may beidentical or non-identical in configuration (e.g., it is envisioned thatthe temperature control system 200 may include TECs 206 that vary insize) and/or that the TECs 206 may be arranged in series or in parallel(e.g., in a stacked configuration).

As indicated above, embodiments of the disclosure are envisioned hereinin which the temperature control system 200 may be configured to heat,rather than cool, the power source 14 of the UAV 10 when the UAV 10 isdocked in the base station 100. In such embodiments, current flowthrough the TEC 206 can be reversed (e.g., via electronic control) suchthat the first end 240 of the TEC 206 functions as the “cold” end andthe second end 242 of the TEC 206 functions as the “hot” end.

During use of the temperature control system 200, the upper air circuit202 draws air in from the ambient, either from within the base station100 or externally of the base station 100, which is directed across theupper heat sink 212 via the upper air circulator 210. As the air flowsacross the upper heat sink 212, heat is withdrawn, thereby cooling theupper heat sink 212 and, thus, the first (“hot) end 240 of the TEC 206,and heating the air. The heated air is then discharged from the upperair circuit 202, being expelled either into the base station 100 orexternally thereof (e.g., through a vent), and is replaced by coolerambient air that is drawing into the upper air circuit 202 by the upperair circulator 210.

Upon docking of the UAV 10, as the cradle 106 moves from the extendedposition (FIG. 13 ) into the retracted position (FIGS. 2, 10 ), theforward section 230 of the lower plenum 220 mates with (engages) therear section 228, which closes the lower air circuit 204 and allows forthe continuous circulation of air therethrough. To facilitate matingengagement between the forward section 230 and the rear section 228, itis envisioned that the forward section 230 and the rear section 228 mayinclude one or more seals (e.g., O-rings) or corresponding engagementstructures (e.g., collars, flanges, or the like) at the interfacetherebetween.

Air flowing through the lower air circuit 204 is directed across thelower heat sink 224 via the lower air circulator 222, which withdrawsheat from the air to cool the air prior to entering the chamber 142 ofthe cradle 106 via the air inlet 232. As the cooled air flows throughacross the cradle 106 and through the chamber 142, heat is withdrawnfrom the power source 14 (FIGS. 2, 4, 5 ) of the docked UAV 10, which isfacilitated by the heat exchanger 24. More specifically, in theillustrated embodiment, the cooled air flows through the channels 32(FIG. 4 ) defined by the diffusers 26 (e.g., the fins 30), whichincreases the distribution of thermal energy from the power source 14 ofthe UAV 10 to enhance cooling, and increases the temperature of the air.After flowing across the power source 14, the (heated) air exits thechamber 142 via the air outlet 234 and is redirected across the lowerheat sink 224 (e.g., via the lower air circulator 222) to again cool theair prior to recirculation through the cradle 106 and across the powersource 14.

Weather and Climate Management

To allow for operation in various weather conditions, the base station100 includes a plurality of components and systems that are configuredto regulate temperature, moisture, humidity, and the like in order tomaximize operability in a variety of environments.

Snow and Ice

As seen in FIG. 25 , in certain embodiments of the disclosure, the basestation 100 includes one or more heating elements 244 that are thermallyand/or physically connected to (supported by) the enclosure 102 (e.g.,via an adhesive). Although shown as being associated with (supported by)the roof section 176 of the outer housing 110 in the particularembodiment illustrated, it is envisioned that the heating element(s) 244may be thermally and/or physically connected to any section(s) of theouter housing 110 that may benefit from heating. Upon activation, theheating element(s) 244 increase the temperature of (heat) the outerhousing 110 (e.g., to reduce the presence of snow and/or ice on the roofsection 176).

It is envisioned that the heating element(s) 244 may be connected to anysuitable power source, whether internal to the base station 100 (e.g.,to the power supply controlled by the main board/processor) or external(e.g., to a separate power supply, battery, or the like), and that theheating element(s) 244 may be either manually or automaticallyactivated. For example, it is envisioned that the heating element(s) 244may be activated via a signal that is relayed by one or more temperaturesensors 246 that are in communication with the heating element(s) 244and which are configured to detect when the temperature crosses (e.g.,falls below or exceeds) a predetermined threshold (e.g., 32° F.).Additionally, or alternatively, it is envisioned that the heatingelement(s) 244 may be activated upon receiving an activation signal froma weather station (e.g., via a cloud-based connection) and/or from thevisualization system 174, which may be configured to visually detect thepresence of snow and/or ice.

Internal Temperature and Humidity Regulation

To regulate (control) the temperature and/or humidity within the basestation 100, it is envisioned that the base station 100 may include oneor more internal fans 248 (FIG. 26 ), which may be supported in anysuitable location on the inner housing 108 and/or the outer housing 110.The internal fan(s) 248 regulate (e.g., vary, control) temperatureand/or humidity within the base station 100 and may be configured toeither cool the base station 100 or heat the base station 100 (e.g., viathermal connection to one or more heating elements or components).

The internal fan(s) 248 are controllable (e.g., via the mainboard/processor) to draw air in and exhaust air through one or moreports/vents in the outer housing 110 and/or the inner housing 108, thelocation(s) of which may be varied to direct air flow in a particulardirection (e.g., across the UAV 10). For example, it is envisioned thatthe port(s)/vent(s) may be located and/or configured to create air flowthrough the base station 100 in any effective (or otherwise desired)pattern.

In certain embodiments of the disclosure, it is envisioned that theinternal fan(s) 248 may be automatically activated via a signal that isrelayed by one or more sensors 250 that are configured to detecttemperature, humidity, etc. Additionally, or alternatively, it isenvisioned that the internal fan(s) 248 may be connected to a timer suchthat the internal fan(s) 248 are automatically activated at a particulartime of day.

In the context of humidity regulation, upon the detection of moisture,the sensor(s) 250 may generate an activation signal that can be utilizedto initiate one or more mitigation processes. For example, it isenvisioned that the sensor(s) may be in communication with the internalfan(s) 248 such that the internal fan(s) 248 are engaged upon receipt ofthe activation signal from the sensor(s) 250 to remove (or otherwisemitigate) excess humidity within the base station 100, therebyinhibiting (if not entirely preventing) condensation that mightotherwise compromise the functionality of one or more components of theUAV 10 or the base station 100. For example, the presence ofcondensation may result in malfunction and/or damage to the electronicsmodule (e.g., the main board/processor) and/or “fogging” of thevisualization system 174. To further inhibit (if not entirely prevent)the presence of humidity, condensation, moisture, etc., in certainembodiments of the disclosure, it is envisioned that the electronicsmodule may be sealed within the base station 100. For example, theelectronics module, or the various components thereof (e.g., motordrivers, interface boards, lighting boards, etc.), may be sealed, eithercollectively (via hermetic sealing) or individually (e.g., via dipcoating).

Drainage

In certain embodiments of the disclosure, the enclosure 102 (e.g., theouter housing 110) may include one or more channels 252 (FIG. 27 ) thatare configured to collect and direct water away from any entry pointsinto the enclosure 102 in a manner that inhibits (if not entirelyprevents) entry into the base station 100 and/or away from anycomponents, whether electronic, mechanical, or otherwise, that may becompromised by the presence of moisture. For example, it is envisionedthat the channel(s) 252 may be configured to collect and direct wateraway from the interface with any power cables, any lockingmembers/mechanisms, the door 104 (FIG. 1 ), etc. While the enclosure 102is shown as including a single channel 252 that extends about a rearperiphery 254 of the outer housing 110 in the particular embodimentillustrated, it should be appreciated that the number of channels 252and/or the location of the channels 252 may be varied without departingfrom the present disclosure. For example, embodiments including one ormore additional channels 252 are also envisioned herein, as areembodiments in which the enclosure 102 may include one or more channels252 that extend about a front periphery 256 (FIG. 1 ) of the outerhousing 110, the roof section 176, etc.

In the particular embodiment of the base station 100 illustrated in FIG.27 , the channel 252 is defined by an (molded) insert 258 that isincorporated into the outer housing 110. It is envisioned, however, thatthe channel(s) 252 may be configured in any manner suitable for theintended purpose of collecting and/or directing water in the mannerdescribed herein. For example, embodiments are also envisioned in whichthe channel(s) 252 may be integrally (e.g., monolithically) formed withthe outer housing 110.

In certain embodiments of the disclosure, to further inhibit (if notentirely prevent) water penetration, it is envisioned that the enclosure102 may include one or more seals, gaskets, etc., that are associatedwith the channel(s) 252. For example, it is envisioned that such seals,gaskets, etc., may be positioned about the insert 258 and supported bythe inner housing 108 and/or the outer housing 110.

It should be appreciated that any of the aforementioned componentsand/or systems may be omitted in order to reduce the overall cost andcomplexity of the base station 100. For example, in hot (e.g., desert)climates, it is envisioned that the heating element(s) 244 may beeliminated.

Visualization System

With reference now to FIG. 1 , the visualization system 174 includes adigital image capturing device 260 (e.g., a digital camera) or the like.It is envisioned that the visualization system 174 may be connected toany suitable power source, whether internal to the base station 100(e.g., to the power supply controlled by the main board/processor) orexternal (e.g., to a separate power supply, battery, or the like).

In the particular embodiment of the disclosure illustrated, thevisualization system 174 includes a single digital image capturingdevice 260 that is secured, mounted to, or otherwise supported by theforward frame 116 of the outer housing 110, which supports observationand visual analysis of the environment in which the base station 100 islocated as well as observation and visual analysis of the UAV 10 (FIG. 2) prior to takeoff, during takeoff, and during landing. It should beappreciated, however, that the number of digital image capturing devices260 and/or the location of the digital image capturing device(s) 260 maybe varied in alternate embodiments without departing from the presentdisclosure. For example, embodiments including one or more additionaldigital image capturing devices 260 are also envisioned herein.

During operation of the base station 100, the visualization system 174supports visual inspection of the environment, which not only improvessafety of the base station 100 and the UAV 10 by confirming the absenceof people, animals, etc., prior to takeoff, during takeoff, and duringlanding of the UAV 10, but functionality of the base station 100 aswell. For example, it is envisioned that the visualization system 174may be configured to identify precipitation (e.g., snow, ice, rain,etc.) and actuate (trigger) operation of the heating element(s) 244(FIG. 25 ), the internal fan(s) 248 (FIG. 26 ), or other such systems.It is also envisioned that the visualization system 174 may be utilizedto inspect the UAV 10 (e.g., prior to takeoff and/or during docking) andidentify any damage that may result in subsequent suboptimalperformance.

While the present disclosure has been described in connection withcertain embodiments, it is to be understood that the present disclosureis not to be limited to the disclosed embodiments, but, on the contrary,is intended to cover various modifications and equivalent arrangementsincluded within the scope of the appended claims, which scope is to beaccorded the broadest interpretation so as to encompass all suchmodifications and equivalent structures as is permitted under the law.

Persons skilled in the art will understand that the various embodimentsof the present disclosure and shown in the accompanying figuresconstitute non-limiting examples, and that additional components andfeatures may be added to any of the embodiments discussed hereinabovewithout departing from the scope of the present disclosure.Additionally, persons skilled in the art will understand that theelements and features shown or described in connection with oneembodiment may be combined with those of another embodiment withoutdeparting from the scope of the present disclosure to achieve anydesired result and will appreciate further features and advantages ofthe presently disclosed subject matter based on the descriptionprovided. Variations, combinations, and/or modifications to any of theembodiments and/or features of the embodiments described herein that arewithin the abilities of a person having ordinary skill in the art arealso within the scope of the present disclosure, as are alternativeembodiments that may result from combining, integrating, and/or omittingfeatures from any of the disclosed embodiments.

Use of the term “optionally” with respect to any element of a claimmeans that the element may be included or omitted, with bothalternatives being within the scope of the claim. Additionally, use ofbroader terms such as “comprises,” “includes,” and “having” should beunderstood to provide support for narrower terms such as “consistingof,” “consisting essentially of,” and “comprised substantially of.”Accordingly, the scope of protection is not limited by the descriptionset out above, but is defined by the claims that follow, and includesall equivalents of the subject matter of the claims.

In the preceding description, reference may be made to the spatialrelationship between the various structures illustrated in theaccompanying drawings, and to the spatial orientation of the structures.However, as will be recognized by those skilled in the art after acomplete reading of this disclosure, the structures described herein maybe positioned and oriented in any manner suitable for their intendedpurpose. Thus, the use of terms such as “above,” “below,” “upper,”“lower,” “inner,” “outer,” “left,” “right,” “upward,” “downward,”“inward,” “outward,” “horizontal,” “vertical,” etc., should beunderstood to describe a relative relationship between the structuresand/or a spatial orientation of the structures. Those skilled in the artwill also recognize that the use of such terms may be provided in thecontext of the illustrations provided by the corresponding figure(s).

Additionally, terms such as “approximately,” “generally,”“substantially,” and the like should be understood to allow forvariations in any numerical range or concept with which they areassociated. For example, it is intended that the use of terms such as“approximately” and “generally” should be understood to encompassvariations on the order of 25%, or to allow for manufacturing tolerancesand/or deviations in design.

Although terms such as “first,” “second,” “third,” etc., may be usedherein to describe various operations, elements, components, regions,and/or sections, these operations, elements, components, regions, and/orsections should not be limited by the use of these terms in that theseterms are used to distinguish one operation, element, component, region,or section from another. Thus, unless expressly stated otherwise, afirst operation, element, component, region, or section could be termeda second operation, element, component, region, or section withoutdeparting from the scope of the present disclosure.

Each and every claim is incorporated as further disclosure into thespecification and represents embodiments of the present disclosure.Also, the phrases “at least one of A, B, and C” and “A and/or B and/orC” should each be interpreted to include only A, only B, only C, or anycombination of A, B, and C.

What is claimed is:
 1. A base station for an unmanned aerial vehicle(UAV), the base station comprising: an enclosure; a cradle configuredfor electrical connection to a power source of the UAV during docking tofacilitate charging of the power source, the cradle being movablebetween a retracted position, in which the cradle is positioned withinthe enclosure, and an extended position, in which the cradle ispositioned externally of the enclosure to facilitate docking with theUAV; and a temperature control system connected to the cradle andconfigured to vary temperature of the power source of the UAV, thetemperature control system including: a thermoelectric conditioner (TEC)having a first end and a second end; a first air circuit thermallyconnected to the TEC and configured to regulate temperature of the TEC;and a second air circuit thermally connected to the TEC such that theTEC is located between the first air circuit and the second air circuit,the second air circuit being configured to direct air across the cradleto thereby heat or cool the power source of the UAV when docked with thebase station.
 2. The base station of claim 1, wherein the first aircircuit is configured as an open system and the second air circuit isconfigured as a closed system.
 3. The base station of claim 1, whereinthe TEC is configured as a Peltier system.
 4. The base station of claim1, wherein the first air circuit includes: a first plenum; a first heatsink connected to the first plenum and the first end of the TEC; and afirst air circulator configured to direct air through the first plenumand across the first heat sink to vary air temperature within the firstair circuit and thereby regulate the temperature of the TEC.
 5. The basestation of claim 4, wherein the second air circuit includes: a secondplenum; a second heat sink connected to the second plenum and the secondend of the TEC; and a second air circulator configured to direct airthrough the second plenum and across the second heat sink to vary airtemperature within the second air circuit and thereby heat or cool thepower source of the UAV when docked with the base station.
 6. The basestation of claim 5, wherein the temperature control system is configuredto cool the power source of the UAV when docked with the base station.7. The base station of claim 5, wherein the second plenum defines an airinlet and an air outlet, the air inlet being configured to direct airinto the cradle and across the power source of the UAV and the airoutlet being configured to receive the air directed across the powersource of the UAV and redirect the air across the second heat sink. 8.The base station of claim 7, wherein the second plenum includes a firstsection and a second section that is movable in relation to the firstsection.
 9. The base station of claim 8, wherein the first section isconnected to the TEC and the second section is connected to the cradle.10. The base station of claim 9, wherein the first section and thesecond section are configured for mating engagement upon movement of thecradle into the retracted position.
 11. Abase station for an unmannedaerial vehicle (UAV), the base station comprising: a temperature controlsystem configured to vary temperature of the UAV, the temperaturecontrol system including: a thermoelectric conditioner (TEC); an openair circuit thermally connected to the TEC and configured to regulatetemperature of the TEC; and a closed air circuit thermally connected tothe TEC such that the TEC is located between the open air circuit andthe closed air circuit, the closed air circuit being configured todirect air across the UAV when docked with the base station.
 12. Thebase station of claim 11, wherein the temperature control system isconfigured to heat or cool the UAV subject to environmental conditions.13. The base station of claim 11, wherein the closed air circuitincludes a first section and a second section that is movable inrelation to the first section.
 14. The base station of claim 13, furthercomprising a cradle configured for electrical connection to the UAVduring docking to facilitate charging of the UAV, the cradle beingextendable from and retractable into the base station.
 15. The basestation of claim 14, wherein the first section of the closed air circuitis connected to the TEC and the second section of the closed air circuitis connected to the cradle, the first section and the second sectionbeing configured for mating engagement upon retraction of the cradleinto the base station.
 16. A method of regulating temperature of a powersource in an unmanned aerial vehicle (UAV), the method comprising:docking the UAV within a cradle of a base station; retracting the cradleinto the base station; and directing thermally conditioned air acrossthe power source of the UAV via an air circuit connected to the cradle.17. The method of claim 16, further including directing air across aheat sink thermally connected to a thermoelectric conditioner (TEC) totreat the air prior to direction across the power source of the UAV. 18.The method of claim 17, wherein directing air across the heat sinkincludes circulating the air through a plenum connected to the heatsink.
 19. The method of claim 18, wherein retracting the cradle into thebase station includes closing the air circuit.
 20. The method of claim19, wherein closing the air circuit includes mating a first section ofthe plenum with a second section of the plenum, the first section of theplenum being connected to the TEC and the second section of the plenumbeing connected to the cradle.